JP2986220B2 - System for inserting a member into a composite structure - Google Patents

System for inserting a member into a composite structure

Info

Publication number
JP2986220B2
JP2986220B2 JP9509233A JP50923397A JP2986220B2 JP 2986220 B2 JP2986220 B2 JP 2986220B2 JP 9509233 A JP9509233 A JP 9509233A JP 50923397 A JP50923397 A JP 50923397A JP 2986220 B2 JP2986220 B2 JP 2986220B2
Authority
JP
Japan
Prior art keywords
compressible material
composite structure
pin
pins
laminate
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired - Lifetime
Application number
JP9509233A
Other languages
Japanese (ja)
Other versions
JPH10511052A (en
Inventor
エム フスコ，トーマス
グレン フレイタス，
コンスタンス マギー，
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
FUOSUTAA MIRAA Inc
Original Assignee
FUOSUTAA MIRAA Inc
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by FUOSUTAA MIRAA Inc filed Critical FUOSUTAA MIRAA Inc
Publication of JPH10511052A publication Critical patent/JPH10511052A/en
Application granted granted Critical
Publication of JP2986220B2 publication Critical patent/JP2986220B2/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C65/00—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor
    • B29C65/56—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using mechanical means or mechanical connections, e.g. form-fits
    • B29C65/562—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using mechanical means or mechanical connections, e.g. form-fits using extra joining elements, i.e. which are not integral with the parts to be joined
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B5/00—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts
    • B32B5/02—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by structural features of a fibrous or filamentary layer
    • B32B5/06—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by structural features of a fibrous or filamentary layer characterised by a fibrous or filamentary layer mechanically connected, e.g. by needling to another layer, e.g. of fibres, of paper
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C65/00—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor
    • B29C65/56—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using mechanical means or mechanical connections, e.g. form-fits
    • B29C65/562—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using mechanical means or mechanical connections, e.g. form-fits using extra joining elements, i.e. which are not integral with the parts to be joined
    • B29C65/564—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using mechanical means or mechanical connections, e.g. form-fits using extra joining elements, i.e. which are not integral with the parts to be joined hidden in the joint, e.g. dowels or Z-pins
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C65/00—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor
    • B29C65/56—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using mechanical means or mechanical connections, e.g. form-fits
    • B29C65/64—Joining a non-plastics element to a plastics element, e.g. by force
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C66/00—General aspects of processes or apparatus for joining preformed parts
    • B29C66/01—General aspects dealing with the joint area or with the area to be joined
    • B29C66/05—Particular design of joint configurations
    • B29C66/10—Particular design of joint configurations particular design of the joint cross-sections
    • B29C66/11—Joint cross-sections comprising a single joint-segment, i.e. one of the parts to be joined comprising a single joint-segment in the joint cross-section
    • B29C66/112—Single lapped joints
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C66/00—General aspects of processes or apparatus for joining preformed parts
    • B29C66/01—General aspects dealing with the joint area or with the area to be joined
    • B29C66/05—Particular design of joint configurations
    • B29C66/10—Particular design of joint configurations particular design of the joint cross-sections
    • B29C66/11—Joint cross-sections comprising a single joint-segment, i.e. one of the parts to be joined comprising a single joint-segment in the joint cross-section
    • B29C66/112—Single lapped joints
    • B29C66/1122—Single lap to lap joints, i.e. overlap joints
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C66/00—General aspects of processes or apparatus for joining preformed parts
    • B29C66/01—General aspects dealing with the joint area or with the area to be joined
    • B29C66/05—Particular design of joint configurations
    • B29C66/10—Particular design of joint configurations particular design of the joint cross-sections
    • B29C66/13—Single flanged joints; Fin-type joints; Single hem joints; Edge joints; Interpenetrating fingered joints; Other specific particular designs of joint cross-sections not provided for in groups B29C66/11 - B29C66/12
    • B29C66/131—Single flanged joints, i.e. one of the parts to be joined being rigid and flanged in the joint area
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C66/00—General aspects of processes or apparatus for joining preformed parts
    • B29C66/40—General aspects of joining substantially flat articles, e.g. plates, sheets or web-like materials; Making flat seams in tubular or hollow articles; Joining single elements to substantially flat surfaces
    • B29C66/41—Joining substantially flat articles ; Making flat seams in tubular or hollow articles
    • B29C66/43—Joining a relatively small portion of the surface of said articles
    • B29C66/434—Joining substantially flat articles for forming corner connections, fork connections or cross connections
    • B29C66/4344—Joining substantially flat articles for forming fork connections, e.g. for making Y-shaped pieces
    • B29C66/43441—Joining substantially flat articles for forming fork connections, e.g. for making Y-shaped pieces with two right angles, e.g. for making T-shaped pieces, H-shaped pieces
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C66/00—General aspects of processes or apparatus for joining preformed parts
    • B29C66/40—General aspects of joining substantially flat articles, e.g. plates, sheets or web-like materials; Making flat seams in tubular or hollow articles; Joining single elements to substantially flat surfaces
    • B29C66/41—Joining substantially flat articles ; Making flat seams in tubular or hollow articles
    • B29C66/45—Joining of substantially the whole surface of the articles
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C66/00—General aspects of processes or apparatus for joining preformed parts
    • B29C66/70—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material
    • B29C66/72—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material characterised by the structure of the material of the parts to be joined
    • B29C66/721—Fibre-reinforced materials
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C66/00—General aspects of processes or apparatus for joining preformed parts
    • B29C66/70—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material
    • B29C66/72—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material characterised by the structure of the material of the parts to be joined
    • B29C66/723—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material characterised by the structure of the material of the parts to be joined being multi-layered
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C66/00—General aspects of processes or apparatus for joining preformed parts
    • B29C66/80—General aspects of machine operations or constructions and parts thereof
    • B29C66/83—General aspects of machine operations or constructions and parts thereof characterised by the movement of the joining or pressing tools
    • B29C66/832—Reciprocating joining or pressing tools
    • B29C66/8322—Joining or pressing tools reciprocating along one axis
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
    • B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
    • B29C70/06—Fibrous reinforcements only
    • B29C70/10—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres
    • B29C70/16—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres using fibres of substantial or continuous length
    • B29C70/24—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres using fibres of substantial or continuous length oriented in at least three directions forming a three dimensional structure
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
    • B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
    • B29C70/28—Shaping operations therefor
    • B29C70/54—Component parts, details or accessories; Auxiliary operations, e.g. feeding or storage of prepregs or SMC after impregnation or during ageing
    • B29C70/543—Fixing the position or configuration of fibrous reinforcements before or during moulding
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B3/00—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shape; Layered products comprising a layer having particular features of form
    • B32B3/02—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shape; Layered products comprising a layer having particular features of form characterised by features of form at particular places, e.g. in edge regions
    • B32B3/08—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shape; Layered products comprising a layer having particular features of form characterised by features of form at particular places, e.g. in edge regions characterised by added members at particular parts
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B5/00—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts
    • B32B5/22—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by the presence of two or more layers which are next to each other and are fibrous, filamentary, formed of particles or foamed
    • B32B5/24—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by the presence of two or more layers which are next to each other and are fibrous, filamentary, formed of particles or foamed one layer being a fibrous or filamentary layer
    • B32B5/26—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by the presence of two or more layers which are next to each other and are fibrous, filamentary, formed of particles or foamed one layer being a fibrous or filamentary layer another layer next to it also being fibrous or filamentary
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B7/00—Layered products characterised by the relation between layers; Layered products characterised by the relative orientation of features between layers, or by the relative values of a measurable parameter between layers, i.e. products comprising layers having different physical, chemical or physicochemical properties; Layered products characterised by the interconnection of layers
    • B32B7/04—Interconnection of layers
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C2791/00—Shaping characteristics in general
    • B29C2791/004—Shaping under special conditions
    • B29C2791/008—Using vibrations during moulding
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C65/00—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor
    • B29C65/56—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using mechanical means or mechanical connections, e.g. form-fits
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C66/00—General aspects of processes or apparatus for joining preformed parts
    • B29C66/70—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material
    • B29C66/71—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material characterised by the composition of the plastics material of the parts to be joined
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C66/00—General aspects of processes or apparatus for joining preformed parts
    • B29C66/70—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material
    • B29C66/72—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material characterised by the structure of the material of the parts to be joined
    • B29C66/727—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material characterised by the structure of the material of the parts to be joined being porous, e.g. foam
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C66/00—General aspects of processes or apparatus for joining preformed parts
    • B29C66/70—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material
    • B29C66/74—Joining plastics material to non-plastics material
    • B29C66/742—Joining plastics material to non-plastics material to metals or their alloys
    • B29C66/7422—Aluminium or alloys of aluminium
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C66/00—General aspects of processes or apparatus for joining preformed parts
    • B29C66/70—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material
    • B29C66/74—Joining plastics material to non-plastics material
    • B29C66/742—Joining plastics material to non-plastics material to metals or their alloys
    • B29C66/7428—Transition metals or their alloys
    • B29C66/74283—Iron or alloys of iron, e.g. steel
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C66/00—General aspects of processes or apparatus for joining preformed parts
    • B29C66/70—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material
    • B29C66/74—Joining plastics material to non-plastics material
    • B29C66/744—Joining plastics material to non-plastics material to elements other than metals
    • B29C66/7442—Boron
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C66/00—General aspects of processes or apparatus for joining preformed parts
    • B29C66/70—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material
    • B29C66/74—Joining plastics material to non-plastics material
    • B29C66/746—Joining plastics material to non-plastics material to inorganic materials not provided for in groups B29C66/742 - B29C66/744
    • B29C66/7461—Ceramics
    • B29C66/74611—Carbides; Nitrides
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C66/00—General aspects of processes or apparatus for joining preformed parts
    • B29C66/70—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material
    • B29C66/74—Joining plastics material to non-plastics material
    • B29C66/746—Joining plastics material to non-plastics material to inorganic materials not provided for in groups B29C66/742 - B29C66/744
    • B29C66/7465—Glass
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B2310/00—Treatment by energy or chemical effects
    • B32B2310/028—Treatment by energy or chemical effects using vibration, e.g. sonic or ultrasonic

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Textile Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Composite Materials (AREA)
  • Lining Or Joining Of Plastics Or The Like (AREA)
  • Moulding By Coating Moulds (AREA)
  • Laminated Bodies (AREA)

Description

【発明の詳細な説明】 発明の属する技術分野 本発明は、超音波エネルギーおよび圧力を利用して、
複合構造内に補強部材を挿入するための方法およびシス
テムに関するものである。Description: TECHNICAL FIELD The present invention relates to the use of ultrasonic energy and pressure.
A method and system for inserting a stiffening member into a composite structure.

発明の背景 強度対重量比が大きいことにより、複合構造が使用さ
れる。しかしながら、複合部材の固定方法が、しばしば
問題となる。例えば、航空機の構造用スキン部材を支持
ストリンガーに対して取り付けるには、ボルトおよび／
またはリベットを使用することができる。しかし、この
ような固定であると、重量が増加してしまったり、製造
コストが増大してしまったり、さらに、ラミネート複合
体の層どうし間における局所破損モードに寄与してしま
ったりする。また、２つの複合部材を連結するために、
半田づけが使用される（米国特許明細書第5,021,107号
参照）。しかし、負荷がかかった場合に２つの複合部材
間の完全な連結を維持し得るほどの十分な強度が、常に
得られるわけではない。BACKGROUND OF THE INVENTION Due to the high strength-to-weight ratio, composite structures are used. However, the method of fixing the composite member is often problematic. For example, to attach an aircraft structural skin member to a support stringer, bolts and / or
Or rivets can be used. However, such anchoring increases weight, increases manufacturing costs, and contributes to local failure modes between layers of the laminate composite. Also, to connect the two composite members,
Soldering is used (see US Pat. No. 5,021,107). However, sufficient strength is not always available to maintain a perfect connection between the two composite members under load.

本出願人は、構造部材の厚さ方向に貫通させて、ボロ
ンファイバのようなピンを挿入することにより、剥離や
クラックを防止するための複合構造の補強が行えること
を、見い出した。ピンは、熱的に減圧可能なフォームボ
ディ内に挿入され、フォームボディは、複合部材上に配
置される。オートクレーブ内において、印加する温度お
よび圧力を増大させることにより、ピンを複合部材の厚
さ方向に挿入することができる。これに関しては、米国
特許明細書第4,808,461号を参照されたい。The present applicant has found that a composite structure for preventing peeling and cracking can be reinforced by inserting a pin such as a boron fiber through the structural member in the thickness direction. The pins are inserted into a thermally decompressible foam body, which is disposed on the composite member. By increasing the applied temperature and pressure in the autoclave, the pins can be inserted in the thickness direction of the composite member. See in this connection U.S. Pat. No. 4,808,461.

近年、本出願人によって、ピンを互いに連結すべき２
つの複合構造内に挿入し得ること、および、２つの接合
体を貫通して延在しているピンによって連結されたこの
ような構造は、半田づけだけによって形成された連結構
造よりも強度が大きいこと、および、固定手段としての
リベットやボルトに対して意義深い利益をもたらし得る
こと、が示された。これに関しては、米国特許出願第08
/056,029号および米国特許明細書第5,186,776号を参照
されたい。In recent years, the applicant has determined that two pins should be connected to each other.
This structure, which can be inserted into two composite structures and connected by pins extending through the two joints, is stronger than a connection structure formed only by soldering It has been shown that rivets and bolts as fixing means can provide significant benefits. In this regard, U.S. patent application Ser.
See U.S. Patent No. 5,186,776 and U.S. Patent No. 5,186,776.

さらに、従来技術においては、航空機ウィングのスキ
ン／ストリンガー構造のような複合構造を連結するため
のピンの挿入方法において、簡便さを欠いている。とい
うのは、このような構造は、そう簡単には、オートクレ
ーブ内に入らないからである。Furthermore, the prior art lacks simplicity in the method of inserting pins to connect composite structures such as the skin / stringer structure of an aircraft wing. This is because such a structure does not enter the autoclave so easily.

発明の概要 したがって、本発明の目的は、複合材料内へと補強ピ
ンを挿入するための改良された方法およびシステムを提
供することである。SUMMARY OF THE INVENTION Accordingly, it is an object of the present invention to provide an improved method and system for inserting a stiffening pin into a composite material.

また、本発明の目的は、オートクレーブを使用する必
要がないような、また、オートクレーブ内で使用される
温度を上げる必要がないような、複合構造内へと補強ピ
ンを挿入するための方法およびシステムを提供すること
である。It is also an object of the present invention to provide a method and system for inserting a reinforcing pin into a composite structure such that there is no need to use an autoclave and no need to increase the temperature used in the autoclave. It is to provide.

また、本発明の目的は、１つの複合ラミネートを他の
複合ラミネートに対して連結するのに使用可能な、半田
づけや、リベットタイプまたはボルトタイプの固定手段
を使用することなく、複合ラミネートどうしの間に連結
を形成し得るような、複合構造内へと補強ピンを挿入す
るための方法およびシステムを提供することである。It is also an object of the present invention to provide a method of connecting composite laminates without the use of soldering or rivet-type or bolt-type fixing means that can be used to join one composite laminate to another. An object is to provide a method and system for inserting a stiffening pin into a composite structure, such that a connection can be formed therebetween.

また、本発明の目的は、複合構造を補強し得るよう
な、複合構造内へと補強ピンを挿入するための方法およ
びシステムを提供することである。It is also an object of the present invention to provide a method and system for inserting reinforcing pins into a composite structure that can reinforce the composite structure.

また、本発明の目的は、製造コストを低減し得るとと
もに、局所破損モードに寄与しないような、複合構造内
へと補強ピンを挿入するための方法およびシステムを提
供することである。It is also an object of the present invention to provide a method and system for inserting a stiffening pin into a composite structure that can reduce manufacturing costs and does not contribute to local failure modes.

本発明は、超音波エネルギーおよび圧力を、複合構造
内にピンを挿入するために利便的に使用することによっ
て得られるものであって、これにより、オートクレーブ
のような、温度と圧力とを増大させるような外部ソース
の必要性を排除し得るものである。本発明においては、
さらに、超音波エネルギーによってピンを加熱する。こ
れにより、ピンを、複合構造内に容易に挿入することが
できる。この場合、複合構造の個々の層を傷めることが
ない。また、挿入時にピン近傍の材料が溶融し、これに
より、２つの複合構造どうしの連結強度をさらに増大さ
せることができる。本発明の方法およびシステムは、２
つの複合部材の連結に、および／または、１つの複合部
材の補強に、使用することができる。The present invention results from the convenient use of ultrasonic energy and pressure to insert a pin into a composite structure, thereby increasing temperature and pressure, such as in an autoclave. The need for such an external source can be eliminated. In the present invention,
Further, the pins are heated by ultrasonic energy. This allows the pins to be easily inserted into the composite structure. In this case, the individual layers of the composite structure are not damaged. Also, the material near the pin melts upon insertion, which can further increase the connection strength between the two composite structures. The method and system of the present invention include:
It can be used for connecting two composite members and / or for reinforcing one composite member.

本発明は、複合構造内に補強ピンを挿入するための方
法およびシステムを、特徴としており、また、好適に備
えている、有している、あるいは、本質的にそのような
方法およびシステムから構成されている。本発明による
方法においては、圧縮性材料内に所定数の補強ピンを挿
入し；圧縮性材料／ピンの組合せ体を複合構造上に配置
し；ピンに対して超音波エネルギーを印加し；同時に、
圧縮性材料に対して圧力を印加し、これにより、圧縮性
材料を押圧してピンを複合構造内に挿入する。The invention features and preferably comprises, has, or consists essentially of, a method and system for inserting a reinforcing pin into a composite structure. Have been. In the method according to the present invention, a predetermined number of reinforcing pins are inserted into the compressible material; placing the compressible material / pin combination on the composite structure; applying ultrasonic energy to the pins;
Pressure is applied to the compressible material, thereby pressing the compressible material and inserting the pin into the composite structure.

圧縮性材料／ピンの組合せ体を複合構造上に配置する
に際しては、圧縮性材料／ピンの組合せ体を、複数のラ
ミネート構造の連結に供される２つまたはそれ以上のラ
ミネート構造どうしの連結領域の近傍に配置する。圧縮
性材料／ピンの組合せ体を複合構造上に配置するに際し
ては、また、圧縮性材料／ピンの組合せ体を、ラミネー
ト構造の補強に供されるラミネート構造の上に配置す
る。複合構造は、加硫されたファイバマトリクス構造と
することができる。複合構造は、また、未加硫のファイ
バマトリクス構造とすることができる。In placing the compressible material / pin combination on the composite structure, the compressible material / pin combination is connected to two or more laminate structures that are used to connect a plurality of laminate structures. Is placed in the vicinity of. In placing the compressible material / pin combination on the composite structure, the compressible material / pin combination is also placed on the laminate structure that serves to reinforce the laminate structure. The composite structure can be a vulcanized fiber matrix structure. The composite structure can also be an unvulcanized fiber matrix structure.

本発明による方法においては、さらに、圧縮性材料へ
の圧力印加時において圧縮性材料内での補強ピンの向き
を適正に維持するために、圧縮性材料の少なくとも一面
に、スクリーン層を付加する。In the method according to the present invention, a screen layer is further added to at least one surface of the compressible material in order to properly maintain the orientation of the reinforcing pin in the compressible material when pressure is applied to the compressible material.

複合構造内に補強ピンを挿入するための本発明による
システムにおいては、圧縮性材料の内部に挿入配置され
た所定数の補強ピンと；ピンに超音波エネルギーを印加
するための超音波デバイスと；圧縮性材料を押圧してピ
ンを複合構造内に挿入するために、超音波エネルギーの
印加と同時に、ピンに対して圧力を印加するための手段
と；を具備している。A system according to the present invention for inserting a stiffening pin into a composite structure includes a predetermined number of stiffening pins inserted within a compressible material; an ultrasonic device for applying ultrasonic energy to the pin; Means for applying pressure to the pin simultaneously with the application of ultrasonic energy to press the conductive material to insert the pin into the composite structure.

複合構造は、連結されるべき少なくとも２つのラミネ
ート構造、あるいは、補強されるべきラミネート構造、
を備えている。複合構造は、加硫されたファイバマトリ
クス構造、あるいは、未加硫のファイバマトリクス構
造、を備えている。The composite structure comprises at least two laminate structures to be connected, or a laminate structure to be reinforced,
It has. The composite structure has a vulcanized fiber matrix structure or an unvulcanized fiber matrix structure.

圧縮性材料は、この圧縮性材料への圧力印加時におい
てこの圧縮性材料内での補強ピンの向きを適正に維持す
るために、圧縮性材料の少なくとも一面に、スクリーン
層を備えることができる。The compressible material may include a screen layer on at least one side of the compressible material to properly maintain the orientation of the reinforcing pins within the compressible material when pressure is applied to the compressible material.

好ましい実施形態の説明 他の目的、特徴点、および、利点は、添付図面を参照
した以下の好ましい実施形態の説明により、当業者であ
れば理解されるであろう。DESCRIPTION OF THE PREFERRED EMBODIMENTS Other objects, features and advantages will be understood by those skilled in the art from the following description of preferred embodiments with reference to the accompanying drawings.

図１は、典型的には航空機ウィング部分をなす、スト
リンガーによって構造的に補強された２つのラミネート
を示す概略的な断面図である。FIG. 1 is a schematic cross-sectional view showing two laminates structurally reinforced by stringers, typically forming part of an aircraft wing.

図2A〜図2Cは、２つのラミネートの厚さ方向に補強ピ
ンを挿入するために使用される方法およびシステムを示
す概略的な断面図である。2A-2C are schematic cross-sectional views illustrating a method and system used to insert a stiffening pin through the thickness of two laminates.

図３は、図2A〜図2Cの方法によって挿入された補強ピ
ンを示す概略的な斜視図であって、２つのラミネート間
に連結を形成する様子が示されている。FIG. 3 is a schematic perspective view showing a reinforcing pin inserted according to the method of FIGS. 2A-2C, showing the formation of a connection between two laminates.

図４は、ラミネートの個々の層を補強するために、単
一のラミネート内に挿入されたピンを示す概略的な斜視
図である。FIG. 4 is a schematic perspective view showing pins inserted into a single laminate to reinforce individual layers of the laminate.

図５は、本発明の超音波ホーンの適用時にピンの向き
を維持するために付加されたスクリーン材料層を備え
た、フォームボディ／ピンの組合せ体を示す概略的な斜
視図である。FIG. 5 is a schematic perspective view showing a foam body / pin combination with an additional layer of screen material to maintain pin orientation during application of the ultrasonic horn of the present invention.

図１は、航空機ウィング部分として知られているよう
な、ストリンガー14によって構造的に補強された２つの
ラミネート10、12を示している。上記の発明の背景の項
で説明したように、ラミネート12をストリンガー14に対
して連結するために、符号16で示すようなボルトタイプ
またはリベットタイプの固定手段を使用すると、重量が
増大してしまったり、製造コストが増大してしまった
り、さらに、ラミネート／ストリンガー界面におけるあ
るいはラミネートの層13、17どうしの間にさえおける局
所破損モードに寄与してしまったりする。他方、すべて
の応用に関して、米国特許明細書第4,808,461号に記載
されているように、ラミネート12とストリンガー14とに
貫通させてピンを挿入するために、オートクレーブを使
用することは、実用的ではない。FIG. 1 shows two laminates 10, 12 structurally reinforced by stringers 14, such as what is known as an aircraft wing section. As described in the Background section above, the use of bolt-type or rivet-type securing means, such as 16 to connect the laminate 12 to the stringer 14, adds weight. This can lead to increased manufacturing costs and also to local failure modes at the laminate / stringer interface or even between layers 13 and 17 of the laminate. On the other hand, for all applications, it is not practical to use an autoclave to insert pins through the laminate 12 and the stringer 14, as described in U.S. Pat.No. 4,808,461. .

本発明においては、図2Aに示すように、複数のピン2
2、24、26が、まず、フォームホディ28内に挿入され、
その後、ラミネート32に対して連結されるべきラミネー
ト30上に、フォ−ムボディ／ピン組合せ体が配置され
る。そして、超音波トランスデューサ34が、ピン22、2
4、26に対して超音波エネルギーを印加するために使用
される。これと同時に、図2Bにおいて力Ｆで示すような
圧力が印加され、フォームボディ28が圧縮されるととも
に、各ラミネートと個別層に劣化をもたらすことなく、
ピン22、24、26が図示のようにラミネート30、32の厚さ
寸法を貫通して挿入される。フォームボディ28は、超音
波エネルギーおよび圧力を印加するステップ時において
は、ピンを便宜的に適正な向きに維持する。また、超音
波エネルギーを使用することにより、図2Cにおいて符号
34、36で示すように、ピン22回りに局所的な溶融が引き
起こされる。このことは、ラミネート30、32間の接合
を、より強力なものとする。In the present invention, as shown in FIG.
2, 24, 26 are first inserted into the foam body 28,
The form body / pin combination is then placed on the laminate 30 to be joined to the laminate 32. Then, the ultrasonic transducer 34 is connected to the pins 22, 2
Used to apply ultrasonic energy to 4,26. At the same time, a pressure as shown by force F in FIG. 2B is applied to compress the foam body 28 and without degrading each laminate and the individual layers.
Pins 22, 24, 26 are inserted through the thickness dimension of laminates 30, 32 as shown. The foam body 28 conveniently maintains the pins in the proper orientation during the step of applying ultrasonic energy and pressure. Also, by using ultrasonic energy,
Local melting is caused around the pin 22, as shown at 34,36. This makes the bond between the laminates 30, 32 stronger.

このようにして、ラミネート30がラミネート32に対し
て（あるいは、図１においては、ラミネート10、12がス
トリンガー14に対して）、ボルトタイプまたはリベット
タイプの固定手段を使用することなく、また、ラミネー
トの個々の層を一切劣化させることなく、連結される。In this way, the laminate 30 can be attached to the laminate 32 (or, in FIG. 1, the laminates 10, 12 to the stringer 14) without using bolt-type or rivet-type fastening means, and Without degrading any of the individual layers.

図３には、図2A〜図2Cを参照して上述した方法に基づ
いて超音波エネルギーおよび圧力を使用することによ
り、図示のように、一端において列をなすピン44、46、
48によって、また、他端において列をなすピン50、52、
54によって、連結された２つの複合材料を示している
（ピンを同じ高さに揃えた後の様子が図示されてい
る）。FIG. 3 illustrates the use of ultrasonic energy and pressure based on the method described above with reference to FIGS. 2A-2C to form a row of pins 44, 46 at one end, as shown.
48, and at the other end, a row of pins 50, 52,
Reference numeral 54 indicates the two composite materials connected to each other (shown after the pins are aligned at the same height).

また、図４に示すように、単一のラミネート60を、図
示のように、列をなすピン62、64を挿入することによっ
て補強することができる。この補強により、オートクレ
ーブを使用することなく、米国特許明細書第4,808,461
号に記載されているように、ラミネート60をｚ方向に補
強することができる。Also, as shown in FIG. 4, a single laminate 60 can be reinforced by inserting rows of pins 62, 64 as shown. This reinforcement allows the use of U.S. Pat. No. 4,808,461 without the use of an autoclave.
The laminate 60 can be reinforced in the z-direction as described in the item.

図2Aに示すようなボディ28は、RTVシリコンラバーの
ような弾性材料、FIBER FORM（登録商標）グラファイ
ト絶縁、KAWOOL（登録商標）セラミクス絶縁、フェノー
ルをベースとするとフォーム、ファイバガラス、ポリア
ミドをベースとする絶縁、メラミン、Rohacell（登録商
標）、Polymathacrylimide（登録商標）、Diveneycell
（登録商標）、クロスリンクしたポリビニル、Klegecel
l（登録商標）をベースとした堅固なポリ塩化ビニル、
フォーム、PVC（ポリ塩化ビニル）、ポリエステル、ポ
リエチレン、ポリプロピレン、ポリウレタン、ポリスス
チレン、ポリイミド、セルロース、アセテート、シリコ
ーン、ポリベンゾイミダゾール、ポリビニル、PEEK、ポ
リエチルエーテルケトン、PPS、ポリフェロンラインサ
ルファイド（Polyphelonlynesulfide）、カーボン、お
よび、グラファイト、を備えた、圧力下で圧縮可能な材
質とすることができる。The body 28 as shown in FIG. 2A may be made of an elastic material such as RTV silicone rubber, FIBER FORM® graphite insulation, KAWOOL® ceramic insulation, phenol based and foam, fiber glass, polyamide based. Insulation, melamine, Rohacell®, Polymathacrylimide®, Diveneycell
®, cross-linked polyvinyl, Klegecel
l (R) based solid polyvinyl chloride,
Foam, PVC (polyvinyl chloride), polyester, polyethylene, polypropylene, polyurethane, polystyrene, polyimide, cellulose, acetate, silicone, polybenzimidazole, polyvinyl, PEEK, polyethyl ether ketone, PPS, polyphelon line sulfide (Polyphelonlynesulfide), It can be made of a material that can be compressed under pressure and includes carbon and graphite.

補強ピン22、24、26は、アルミニウム、ボロン、カー
ボン、グラファイト、ケブラー、ステンレス鋼、チタ
ン、タングステン、ガラス、シリコンカーバイト、酸化
アルミニウム、窒化アルミニウム、堅固なフェノール、
堅固なポリイミド、堅固なエポキシ、熱プラスチック、
および、このような材料の複合体とすることができる。
補強ピン22、24、26は、数値制御機械や当業者には公知
の他の手段によって、フォームボディ28内に挿入され
る。各々が約0.1mmの直径とされたロッドまたはファイ
バまたはピン22、24、26からなる配列が、約1.5mmのフ
ァイバどうしの間隔でもって、ボディ28内に配置され
る。ピンの直径、長さ、および、配置間隔は、補強され
るべき複合構造の幾何形状、あるいは、形成されるべき
連結の幾何形状に依存する。Reinforcing pins 22, 24, 26 are made of aluminum, boron, carbon, graphite, Kevlar, stainless steel, titanium, tungsten, glass, silicon carbide, aluminum oxide, aluminum nitride, solid phenol,
Solid polyimide, solid epoxy, thermal plastic,
And it can be set as the composite of such materials.
The stiffening pins 22, 24, 26 are inserted into the foam body 28 by a numerical control machine or other means known to those skilled in the art. An array of rods or fibers or pins 22, 24, 26 each having a diameter of about 0.1 mm is disposed within the body 28 with a spacing of about 1.5 mm between the fibers. The diameter, length and spacing of the pins will depend on the geometry of the composite structure to be reinforced or the geometry of the connection to be formed.

ラミネート30、32は、既に加硫された樹脂マトリクス
内のファイバ、プレペグ（prepeg）として組み合わされ
た未加硫樹脂内のファイバ、ファイバ状材料からなるプ
レフォーム材料、および、粘着性付与剤、あるいは、ま
だ含浸されていないつや消しの生ファイバ、から形成さ
れたファイバマトリクス構造することができる。ファイ
バマトリクス構造をなす個々の層を固定するために使用
される樹脂は、エポキシポリマイド（epoxy polymide
s）、ビスマレイミド、フェノール（phenolics）、ポリ
シアヌレート（polycyanurate）、PEEK、ポリエーテル
ケトン、PPS、ポリフェノールサルファイド、AVAMID、
ポリマイド（poylmides）、ポリエステル、および、ビ
ニルエステルとすることができる。Laminates 30 and 32 may include fibers in an already vulcanized resin matrix, fibers in an unvulcanized resin combined as a prepeg, a preform material of fibrous material, and a tackifier, or Fiber matrix structures formed from matte raw fibers, which have not yet been impregnated. The resin used to fix the individual layers of the fiber matrix structure is epoxy polymide.
s), bismaleimide, phenolics, polycyanurate, PEEK, polyetherketone, PPS, polyphenol sulfide, AVAMID,
Polyamides, polyesters, and vinyl esters can be used.

必要に応じて、湾曲形状を有したファイバマトリクス
ラミネート構造が要望された場合には、圧縮可能なフォ
ームボディ28を、連結または補強されるべき複合構造の
外形形状に適合するように、熱形成することができる。
図2Aに示すような超音波トランスデューサ34は、Branso
m社から入手可能なモデルTW2であり、これには、Branso
m社の電源であるモデルE150が接続されている。超音波
トランスデューサ34は、所定長さのScotchテープでもっ
て、フォームボディ／ピンの組合せ体がラミネート30、
32の近傍に固定された後に、ドリルプレス内において、
フォームボディ28上に配置された。その後、超音波トラ
ンスデューサが20kHzの周波数にまで励起され、約20〜3
0ft.lb.くらいの印加圧力でもって、ドリルプレスを使
用して、フォームボディを押圧した。ホーン34の先端35
の面接は、幅.5″かつ長さ.435″に限定され、同時に約
４つのピンを挿入するために使用された。パワーおよび
溶着時間は、特定の用途に応じて変化させることができ
る。実施例においては、75％のパワーおよび2.0secの溶
着時間であると、プレフォーム内のステンレス鋼製のま
たは同様のピンを、複合材料内に挿入するに際して、良
好な結果が得られることがわかった。If desired, if a fiber matrix laminate structure having a curved shape is desired, the compressible foam body 28 is thermoformed to match the external shape of the composite structure to be connected or reinforced. be able to.
The ultrasonic transducer 34 as shown in FIG.
Model TW2, available from m.
Model E150, which is the power supply of Company m, is connected. The ultrasonic transducer 34 has a predetermined length of Scotch tape, and a foam body / pin combination is laminated 30,
After being fixed near 32, in the drill press,
Arranged on the foam body 28. After that, the ultrasonic transducer is excited to a frequency of 20 kHz, about 20-3
The foam body was pressed using a drill press with an applied pressure of about 0 ft.lb. Horn 34 tip 35
The interview was limited to .5 "wide and .435" long and was used to insert approximately four pins at the same time. Power and welding time can be varied depending on the particular application. In the examples, a power of 75% and a welding time of 2.0 sec have been found to give good results when inserting stainless steel or similar pins in the preform into the composite. Was.

その結果、連結された複合材料構造、および／また
は、補強された複合構造が得られる。この場合、オート
クレーブを使用する必要がなく、温度を上げる必要もな
い。また、ボルトやリベットといった従来の固定手段を
使用した際に固有の限定も存在しない。The result is a connected composite material structure and / or a reinforced composite structure. In this case, there is no need to use an autoclave and no need to raise the temperature. Also, there is no inherent limitation when using conventional fixing means such as bolts and rivets.

図５に示すように、フォームボディ70内におけるピン
72の配列が比較的厚くなってしまうような場合には、圧
力印加の下で超音波トランスデューサを適用した時に、
ピンがフォームボディ構造の質を落とし、フォームボデ
ィがピンを適正な位置に支持することが困難となってし
まう。したがって、本発明のある実施形態においては、
スクリーン層76をフォームボディに配置して、ピン72、
74を、図示のように、スクリーン層76の格子内に挿入す
る。このようにすれば、圧力印加時に、スクリーン層に
よって、ピンを適正な向きに維持することができる。ま
た、フォームボディの反対側に、他のスクリーン層（図
示せず）を設けることもできる。As shown in FIG. 5, the pins in the foam body 70
If the arrangement of 72 becomes relatively thick, when applying the ultrasonic transducer under pressure,
The pins degrade the quality of the foam body structure, making it difficult for the foam body to support the pins in the proper position. Thus, in one embodiment of the present invention,
Place screen layer 76 on the foam body, pin 72,
74 is inserted into the grid of screen layer 76 as shown. In this case, the pins can be maintained in an appropriate direction by the screen layer when pressure is applied. Also, another screen layer (not shown) can be provided on the opposite side of the foam body.

本発明の特定の特徴点について例示したけれども、こ
の例示は、便宜的なものに過ぎず、いくつかの特徴点
を、本発明のいくつかのまたはすべての特徴点と任意に
組み合わせることができる。Although illustrated with particular features of the present invention, this illustration is for convenience only and some features may be arbitrarily combined with some or all features of the present invention.

当業者であれば、添付の請求範囲内において、他の形
態を採用することができる。A person skilled in the art can adopt other forms within the scope of the attached claims.

フロントページの続き (72)発明者 マギー， コンスタンス アメリカ合衆国 マサチューセッツ 01460 リットルトン フォスター ス トリート 63 (58)調査した分野(Int.Cl.6，ＤＢ名) B32B 1/00 - 35/00 Continued on the front page (72) Inventor Maggie, Constance United States Massachusetts 01460 Liters Foster Street 63 (58) Fields studied (Int. Cl. 6 , DB name) B32B 1/00-35/00

Claims (12)

(57)【特許請求の範囲】(57) [Claims] 【請求項１】複合構造内に補強ピンを挿入するための方
法であって、 圧縮性材料内に所定数の補強ピンを挿入して圧縮性材料
／ピンの組合せ体を形成し； 前記圧縮性材料／ピンの組合せ体を、樹脂マトリクス内
にファイバを有してなる複数の層を備えてなる複合構造
上に、配置し、； 前記ピンに対して超音波エネルギーを印加し； 同時に、前記圧縮性材料に対して圧力を印加し、これに
より、前記圧縮性材料を押圧して前記ピンを前記複合構
造内に挿入することを特徴とする方法。1. A method for inserting a reinforcing pin into a composite structure, comprising: inserting a predetermined number of reinforcing pins into a compressible material to form a compressible material / pin combination; Placing a material / pin combination on a composite structure comprising a plurality of layers having fibers in a resin matrix; applying ultrasonic energy to said pins; Applying pressure to a compressible material, thereby pressing the compressible material and inserting the pin into the composite structure. 【請求項２】圧縮性材料／ピンの組合せ体を複合構造上
に配置するに際しては、前記圧縮性材料／ピンの組合せ
体を、複数のラミネート構造の連結に供される２つまた
はそれ以上のラミネート構造どうしの連結領域の近傍に
配置することを特徴とする請求項１記載の方法。2. In placing the compressible material / pin combination on a composite structure, the compressible material / pin combination may be used to connect two or more laminate structures to one another. The method according to claim 1, wherein the first and second laminate structures are disposed in the vicinity of a connection region. 【請求項３】圧縮性材料／ピンの組合せ体を複合構造上
に配置するに際しては、前記圧縮性材料／ピンの組合せ
体を、ラミネート構造の補強に供されるラミネート構造
の上に配置することを特徴とする請求項１記載の方法。3. When arranging the compressible material / pin combination on the composite structure, arranging the compressible material / pin combination on the laminate structure used for reinforcing the laminate structure. The method of claim 1, wherein: 【請求項４】前記複合構造が、前記樹脂マトリクスが加
硫されている、加硫されたファイバマトリクス構造を備
えていることを特徴とする請求項１記載の方法。4. The method of claim 1 wherein said composite structure comprises a vulcanized fiber matrix structure wherein said resin matrix is vulcanized. 【請求項５】前記複合構造が、前記樹脂マトリクスが加
硫されていない、未加硫のファイバマトリクス構造を備
えていることを特徴とする請求項１記載の方法。5. The method of claim 1 wherein said composite structure comprises an uncured fiber matrix structure wherein said resin matrix is uncured. 【請求項６】さらに、 前記圧縮性材料への圧力印加時において前記圧縮性材料
内での前記補強ピンの向きを適正に維持するために、前
記圧縮性材料の少なくとも一面に、スクリーン層を付加
することを特徴とする請求項１記載の方法。6. A screen layer is added to at least one surface of the compressible material so as to properly maintain the orientation of the reinforcing pin in the compressible material when pressure is applied to the compressible material. The method of claim 1, wherein 【請求項７】樹脂マトリクス内にファイバを有してなる
複数の層を備えてなる複合構造内に、補強ピンを挿入す
るためのシステムであって、 内部に所定数の補強ピンが配置された圧縮性材料と； 前記ピンに超音波エネルギーを印加するための超音波デ
バイスと； 前記圧縮性材料を押圧して前記ピンを前記複合構造内に
挿入するために、超音波エネルギーの印加と同時に、前
記ピンに対して圧力を印加するための手段と； を具備することを特徴とするシステム。7. A system for inserting reinforcing pins into a composite structure comprising a plurality of layers having fibers in a resin matrix, wherein a predetermined number of reinforcing pins are disposed inside. An ultrasonic device for applying ultrasonic energy to the pin; and simultaneously applying ultrasonic energy to press the compressible material and insert the pin into the composite structure; Means for applying pressure to said pins. 【請求項８】前記複合構造は、連結されるべき少なくと
も２つのラミネート構造を備えていることを特徴とする
請求項７記載のシステム。8. The system of claim 7, wherein said composite structure comprises at least two laminate structures to be connected. 【請求項９】前記複合構造は、補強されるべきラミネー
ト構造を備えていることを特徴とする請求項７記載のシ
ステム。9. The system of claim 7, wherein said composite structure comprises a laminate structure to be reinforced. 【請求項１０】前記複合構造は、前記樹脂マトリクスが
加硫されている、加硫されたファイバマトリクス構造を
備えていることを特徴とする請求項７記載のシステム。10. The system of claim 7, wherein said composite structure comprises a vulcanized fiber matrix structure wherein said resin matrix is vulcanized. 【請求項１１】前記複合構造は、前記樹脂マトリクスが
加硫されていない、未加硫のファイバマトリクス構造を
備えていることを特徴とする請求項７記載のシステム。11. The system of claim 7, wherein said composite structure comprises an uncured fiber matrix structure wherein said resin matrix is uncured. 【請求項１２】前記圧縮性材料は、この圧縮性材料への
圧力印加時においてこの圧縮性材料内での前記補強ピン
の向きを適正に維持するために、前記圧縮性材料の少な
くとも一面に、スクリーン層を備えていることを特徴と
する請求項７記載のシステム。12. The compressible material may include at least one surface of the compressible material for maintaining proper orientation of the reinforcing pin in the compressible material when pressure is applied to the compressible material. The system of claim 7, comprising a screen layer.
JP9509233A 1995-08-21 1995-08-21 System for inserting a member into a composite structure Expired - Lifetime JP2986220B2 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
PCT/US1995/010654 WO1997006948A1 (en) 1995-08-21 1995-08-21 System for inserting elements in composite structure
US08/600,473 US5589015A (en) 1994-06-07 1996-02-13 Method and system for inserting reinforcing elements in a composite structure

Publications (2)

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JPH10511052A JPH10511052A (en) 1998-10-27
JP2986220B2 true JP2986220B2 (en) 1999-12-06

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EP (1) EP0863811B1 (en)
JP (1) JP2986220B2 (en)
AU (1) AU3411395A (en)
CA (1) CA2229996C (en)
DE (1) DE69531963T2 (en)
ES (1) ES2208694T3 (en)
WO (1) WO1997006948A1 (en)

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
KR100932302B1 (en) * 2007-09-17 2009-12-16 한국항공우주연구원 Composite laminated structure reinforced with performance by pinning, composite manufacturing method, device and manufacturing method of the composite laminated structure
KR101836612B1 (en) * 2016-04-07 2018-03-09 현대자동차주식회사 Hardware combination structure and manufacturing method of the same

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CA2229996A1 (en) 1997-02-27
WO1997006948A1 (en) 1997-02-27
DE69531963D1 (en) 2003-11-20
CA2229996C (en) 2001-06-05
US5589015A (en) 1996-12-31
ES2208694T3 (en) 2004-06-16
DE69531963T2 (en) 2004-07-29
JPH10511052A (en) 1998-10-27
EP0863811A1 (en) 1998-09-16
EP0863811B1 (en) 2003-10-15
AU3411395A (en) 1997-03-12
EP0863811A4 (en) 1998-12-09

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